757
MAINTENANCE MANUAL

 (7)  
07 SERVO AIL

 (a)  
Displays any FCC self-test faults and FCC interface faults related to aileron servos.

 (b)  
Provides interaction message to verify hydraulic pressure on (VFY HYD ON).

 (c)  
Provides interaction message to verify aileron trim set to zero.

 (d)  
GUN 051; provide interaction message to position MCP CMD bat handle switches up to CMD. This action automatically synchronizes the aileron and elevator servos to the present control surface position. Servos will not engage until servos synchronized.

 (e)  
GUN 001-050, 052-999; provide interaction message to push MCP CMD switches. This action automatically synchronizes the aileron and elevator servos to the present control surface position. Servos will not engage until servos synchronized.

 (f)  
Wheel centers, then moves clockwise and then counterclockwise and back to center. Inboard ailerons are driven to a plus and minus 10 degree position. FCC's check that each position is within limits.

 (8)  
08 SERVO ELEV

 (a)  
Displays any FCC self-test faults and FCC interface faults related to elevator servo.

 (b)  
Provides interaction message to verify hydraulic pressure on (VFY HYD ON).

 (c)  
Provides interaction message to verify elevator trim set to zero.

 (d)  
Displays elevator feel position pressure for operator to verify pitot pressure is zero.

 (e)  
GUN 051; provide interaction message to position MCP CMD bat handle switches up to CMD. This action automatically synchronizes the aileron and elevator servos to the present control surface position. Servos will not engage until servos synchronized.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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757
MAINTENANCE MANUAL

 (f)  
GUN 001-050, 052-999; provide interaction message to push MCP CMD switches. This action automatically synchronizes the aileron and elevator servos to the present control surface position. Servos will not engage until servos synchronized.

 (g)  
Column centers, then moves aft (trailing edge up), then forward (trailing edge down) and back to center. Elevators are driven to a plus 20 degrees (trailing edge up) and a minus 9 degrees (trailing edge down) and the FCCs check that each position of the elevator servos and neutral shift tranducers (FEEL POS) are within limits.

 (9)  09 SERVO RUD
 (a)  
Displays any FCC self-test faults and FCC interface faults related to rudder servo.

 (b)  
Provides interaction message to verify hydraulic pressure on (VFY HYD ON).

 (c)  
Provides interaction message to verify rudder trim set to zero.

 (d)  
Rudder centers, then moves rudder trailing edge right, then left and back to center. Rudder driven to a plus and minus 20 degrees and FCCs check that each position is within limits.

 NOTE: Airplanes with -133 FCCs and option group 1 with a value
____ of 6; If the RUD SERVO X FAIL (X = L, C, R) message shows intermittenly when you do this ground test, ignore this message unless the RUD SERVO X FAIL (X = L, C, R) message is shown in the last flight faults or previous flight faults with the diagnostic code 206.
 (10)
 10 SERVO A/T

 (a)  
Displays TMC self-test faults.

 (b)  
Throttle is automatically driven aft for 8 seconds at 10 degrees/second and checked for a Power Lever Angle (PLA) of 44 to 60 degrees. The test fails if the PLA test value is not sensed within six seconds. The autothrottle is then driven forward for eight seconds at 10 degrees/second and checked for a PLA of 120 to 136 degrees, and a tachometer signal feedback of 7 to 12 degrees/second. The autothrottle is driven aft for eight seconds at 10 degrees/second, and checked for a PLA of 44 to 60 degrees, and a tachometer feedback signal of 7 to 12 degrees/second.

 (11)
 11 SW A/P DISC

 (a)  
Displays any FCC self-test faults, and FCC interface faults related to A/P Disc switch.

 (b)  
Instructs the operator to close the captain's and first officer's autopilot disconnect switches. The switch output is monitored for autopilot disconnect command response.
　
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